Detonation stabilization in supersonic flow: effects of suction boundaries
Detonation stabilization in supersonic flow: effects of suction boundaries
In the present work, detonation stabilization in the supersonic flow is numerically investigated in the straight channel with suction boundaries. The two-dimensional reactive Navier–Stokes equations, together with a one-step reaction model, are solved using a second-order-accurate finite volume method solver based on the Structured Adaptive Mesh Refinement framework. The results show that, compared with one jet initiation, detonation initiation can be achieved in a shorter distance using two hot jets subject to the equal total width of the jets. When the suction slots are turned on, the overdriven detonation undergoes a gradual attenuation along with the weakening of the transverse waves, hence leading to dynamic detonation stabilization in the supersonic flow. When the suction slots are closer to the detonation front, the forward propagation of the detonation in the supersonic flow can be more effectively prohibited, implying that the suction slots should be distributed as close as possible to the detonation front in order to realize the maximal suction effect using the minimal suction slots.
1348-1355
Cai, Xiaodong
293bf621-f0e1-48ba-abaa-b41da81ea244
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Liang, Jianhan
fd8229b7-c7f4-4a1b-b94f-abce393f9e9a
Sun, Ming-bo
8bd9b8fe-791b-420d-9f6c-a5cf9a1e1f6a
Dong, Dezun
a82d21ea-89b2-44b4-aabb-4914fb65f6d8
15 March 2020
Cai, Xiaodong
293bf621-f0e1-48ba-abaa-b41da81ea244
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Liang, Jianhan
fd8229b7-c7f4-4a1b-b94f-abce393f9e9a
Sun, Ming-bo
8bd9b8fe-791b-420d-9f6c-a5cf9a1e1f6a
Dong, Dezun
a82d21ea-89b2-44b4-aabb-4914fb65f6d8
Cai, Xiaodong, Deiterding, Ralf, Liang, Jianhan, Sun, Ming-bo and Dong, Dezun
(2020)
Detonation stabilization in supersonic flow: effects of suction boundaries.
AIAA Journal, 58 (3), .
(doi:10.2514/1.J058625).
Abstract
In the present work, detonation stabilization in the supersonic flow is numerically investigated in the straight channel with suction boundaries. The two-dimensional reactive Navier–Stokes equations, together with a one-step reaction model, are solved using a second-order-accurate finite volume method solver based on the Structured Adaptive Mesh Refinement framework. The results show that, compared with one jet initiation, detonation initiation can be achieved in a shorter distance using two hot jets subject to the equal total width of the jets. When the suction slots are turned on, the overdriven detonation undergoes a gradual attenuation along with the weakening of the transverse waves, hence leading to dynamic detonation stabilization in the supersonic flow. When the suction slots are closer to the detonation front, the forward propagation of the detonation in the supersonic flow can be more effectively prohibited, implying that the suction slots should be distributed as close as possible to the detonation front in order to realize the maximal suction effect using the minimal suction slots.
Text
AIAAJ-J058625_AUTHOR_2
- Accepted Manuscript
More information
Accepted/In Press date: 26 November 2019
e-pub ahead of print date: 24 December 2019
Published date: 15 March 2020
Additional Information:
Funding Information:
This work was supported by National Natural Science Foundation of China (No. 11702323), Postdoctoral Innovative Talent Support Program (No. BX20180372), and National Foundation of Defense Technology (No. 3101032).
Publisher Copyright:
© 2019 by the American Institute of Aeronautics and Astronautics, Inc.
Identifiers
Local EPrints ID: 436362
URI: http://eprints.soton.ac.uk/id/eprint/436362
ISSN: 0001-1452
PURE UUID: 9e611ad3-08b0-494b-9a34-fd3a651d6de7
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Date deposited: 09 Dec 2019 17:30
Last modified: 17 Mar 2024 05:07
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Author:
Xiaodong Cai
Author:
Jianhan Liang
Author:
Ming-bo Sun
Author:
Dezun Dong
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